Consider the North American P-51D Mustang. Its wingspan is 37 ft; wing area is 233.6 ft2; and gross weight is 10,100 lb. Assume the Oswald efficiency factor as 0.8. The airplane is flying in steady; level flight at a velocity of 750 mi/h at a standard altitude of 5000 ft. Calculate the drag due to lift using the concept of span loading.

Problem 4: A tourist on the observation deck of the Empire State Building drops a penny. The coin, a disk of diameter D = 0.75 in, thickness h = 0.06 in and density p. = 11.2 slug/ft², falls to the ground from a height of H = 1250 ft at a velocity of U(t). Assuming the penny falls broadside-on it has a drag coefficient given by: 64 *(1+0.138Reg.792) Rep And a reference area of D² A== Area has a density of p. = 2.32*10 slug/ft³ and a viscosity, H.-3.76*10 slug/(ft*s). The gravitational acceleration is g = 32.2 ft/s². Part A: Draw the free body diagram where you show the forces acting on the coin: buoyancy, weight and drag. Part B: Find the coin's terminal velocity and the time it takes to reach the ground (assuming it instantly reaches terminal velocity). Part C: Determine the drag force exerted on the coin. Part D: After reaching its terminal velocity, the coin suddenly undergoes a rotation instability causing it to fall edgewise. What is the new drag force? Ignore pressure drag and…

Consider the NACA 2412 airfoil discussed . The airfoil is flying at a velocity of 60 m/s at a standard altitude of 3 km . The chord length of the airfoil is 2 m. Calculate the lift per unit span when the angle of attack is 4◦.

A light combat aircraft weighs 75,000 N and has a wing area of 27 m?. The maximum lift coefficient with high-lift devices is 1.8, and the structural limit load factor is 6.0. While flying at 250 km/h, the aircraft makes a 90 deg turn in 8 s at sea level holding a constant altitude and at an angle of attack such that the lift-to-drag ratio is 8.0. Find (a) the bank angle, (b) load factor, (c) radius of turn, and (d) the thrust required. [Answer: (a) µ = 54.26 deg, (b) n = 1.7120, (c) R %3D 353.7665 m, and (d) T = 16,050 N.)

Problem 3 - A small airplane that has a mass of 1,500 lb,m is about to take off. The airplane has a coefficient of lift of 1.0 at an Angle of Attack (AOA) of zero and it linearly increases by 0.1 every 10 degrees; wings with a constant chord length of 3.5 ft and a total wingspan of 30 ft; a coefficient of drag of 0.3; and a frontal area of 40 ft? that linearly increases by 5 ft every 10 degrees. If the air is still, and the density of air is 0.076 lbm ft-3 at the ground level what is the critical speed needed for takeoff? If the runway is 1000 ft long, the total coefficient of friction between the road and the airplane is 0.25, what is the average thrust needed to achieve the critical takeoff speed?

Problem 06.025 - Calculate maximum velocity The Predator UAV has the following characteristics: wingspan = 14.85 m, wing area = 11.45 m², maximum weight = 1110 kgf, and fuel weight = 295 kgf. The power plant is a Rotax four- cylinder, four-stroke engine of 100 horsepower driving a two- blade, variable-pitch pusher propeller. Assume: the Oswald efficiency factor is 0.7; the zero-lift drag coefficient is 0.03; the propeller efficiency is 0.9; and the specific fuel consumption is 0.2 kgf of fuel per horsepower per hour. Calculate the maximum velocity of the Predator at sea level. The maximum velocity of the Predator UAV at sea level is m/s.

Thank you!!   An aircraft weighing 65.2 kN when empty has a wing plan form area A of 62.3 m^2 . It cruises at a velocity of 900 km/h and a 4.0 degree angle of attack and altitude of 8500m. Also, the wing characteristics of the airfoil are shown. (a) Determine the allowable weigh of the cargo (b) and if the wingspan s is 20m determine the induce drag coefficient C_Di.

An aircraft is equipped with a wing of symmetrical airfoils. The lift curve slope of the total aircraft is estimated to be 0CL/Oa = 5.0265 1/rad. The stall angle of attack (AOA) is 12°. Wing area is 16 m2. Use g = g0 and r = rO. What is the aircraft's mass during a flight on which a stall speed of 50 kt was observed?

Kindly give me both right solutions with clear calculations  The drag polar of a glider is given by CD=0.01+0.022CL2 . If it is launched from a height of 400m in still air. Please determine:(a) the maximum lift to drag ratio ??;(b) the greatest possible ground distance it can cover.

Consider an airfoil at 12◦ angle of attack. The normal and axial force coefficients are 1.2 and 0.03, respectively. Calculate the lift and drag coefficients.